Arrangement for the cooling of the casing of an aircraft gas turbine engine
US6817189B2 · kind B2 · utility
14Cited by
7References
14Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Aug 31, 2001 |
| Grant date | Nov 16, 2004 |
| Priority date | — |
| Expiry date | Aug 31, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
This invention relates to an arrangement for the cooling of the casing 1 of an aircraft gas turbine with a bypass duct 2 and at least one cooling air tube 3, this cooling air tube 3 having its inlet 4 arranged in the bypass duct 2 and entering at least one cooling air chamber 5 for the supply of cooling air to the casing 1, characterized in that a movable air deflector 6 is arranged in the bypass duct 2 upstream of the inlet 4 of the cooling air tube 3.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.